PWS (20 Dec 2023).pdf

PERFORMANCE WORK STATEMENT

FOR

Contractor-Operated and Maintained Exclusive-Use Type III Helicopter to Support the Air Force Wildland Fire Mission at

Eglin AFB, Tyndall AFB

20 December 2023

Table of Contents

1.0 SECTION I: DESCRIPTION OF SERVICES

1.1 General Scope

1.2 Overview/ Introduction

1.3 Background

1.4 Period of Performance/ Guaranteed Hours

1.5 Place of Performance

1.6 Specific Tasks

1.7 Historical Data

1.8 Minimum Qualifications

1.9 Deliverables

2.0 SECTION II: SERVICE SUMMARY

2.1 General

2.2 Performance Evaluation

2.3 Government Quality Assurance

2.4 Performance Assessment

2.5 Quarterly Progress Meetings

2.6 Contracting Officer’s Representative

2.7 Quality Control

2.8 Contractor’s Performance

3.0 SECTION III: GOVERNMENT FURNISHED PROPERTY and SERVICES

3.1 Government Furnished Services

3.2 Government Furnished Facilities

3.3 Government Furnished Property to include Equipment and Material

4.0 SECTION IV: GENERAL INFORMATION

4.1 Hours of Operation

4.2 Contractor Personnel

4.3 Flight Operations

4.4 Conservation of Utilities

4.5 Environmental Protection

4.6 Miscellaneous Paragraph

4.7 Security

4.8 Safety

5.0 SECTION V APPENDICES & EXHIBITS

APPENDIX 1 Definitions, Abbreviations, and Acronyms APPENDIX 2 Workload Estimates APPENDIX 3 Cargo Hook Requirements EXHIBIT 1 First Aid Kit Aeronautical EXHIBIT 2 Survival Kit Aeronautical (Lower 48) (C-4) EXHIBIT 3 Restraint Systems Conditions Inspection Guidelines (C-4(d)(8)) EXHIBIT 4 Additional Suppression Prescribed Fire Equipment EXHIBIT 5 High Visibility Marking on Main Rotor Blades

SECTION I

1.0 DESCRIPTION OF SERVICES

1.1 General Scope. This is a non-personnel services contract to provide a fully Contractor-operated and maintained exclusive-use Type III helicopter to support the Air Force Wildland Fire Branch mission.

The contractor shall provide a USDA/USDI carded Type III helicopter and USDA/USDI carded pilot to assist in the Air Force Wildland Fire mission, including but not limited to aerial ignition, for prescribed burning a minimum of 90,000 acres per year.

1.1.1 Scope. The intent of this contract is to obtain a fully Contractor- operated and maintained exclusive-use helicopter flight services to support the Air Force Wildland Fire Branch mission. Contractor services will include the following: a helicopter that has been inspected and approved for the mission(s) to be performed and has the ability to obtain an Interagency Helicopter Data Card upon contract award.

Mission(s) to be performed include:

a) Passenger and cargo transport

b) Low-level reconnaissance

c) External load

d) Aerial ignition

e) Fire suppression

f) Water bucket use

g) longline/remote hook

All Contractor furnished pilots must be able to obtain an Interagency Helicopter Pilot Card showing qualifications for the mission(s) to be performed. Missions to be performed include:

a) Low-level reconnaissance

b) Heli tack/passenger transport

c) External load (belly hook)

d) Water delivery

e) Longline/remote hook Vertical Reference (VTR) (150 foot)

f) Aerial ignition using a PSD machine

The Government will direct aircraft to support its missions and objectives. During aerial ignition, the contractor shall maintain the helicopter within GPS boundary parameters as briefed by the Firing Boss in pre-flight briefing.

1.2 Overview/Introduction. The Contractor shall provide all management, personnel, equipment, supplies, facilities, transportation, tools, materials, supervision, and other items and non-personal services necessary to perform helicopter services to support government natural resource missions including aerial ignition as defined in this Performance Work Statement except for those items specified as Government furnished services, equipment and materials. The Contractor shall perform to the standards in this contract. This includes the planning, coordination, and surveillance of the activities necessary to ensure disciplined work performance and timely resources application to accomplish all tasking’s under the contract. The Contractor shall be responsible for maintaining communication with the Contracting Officer (CO) and the Contracting Officer Representative (COR), and to immediately notify both the CO and the COR of any problems that would prevent timely performance of this contract.

1.3 Background. Since 1994, Eglin AFB has used helicopters to implement aerial ignition for wildland fire missions. With a target goal of prescribed burning an average of 90,000 acres per year over a 5-year period, aerial ignition using a helicopter is the safest, most efficient and effective method for accomplishing this mission.

1.4 Period of Performance (PoP) The Contractor shall perform the services in this PWS during the exclusive use period and any services provided during the PoP (see chart below).

Period PoP Start PoP End EU Start EU End Flight Hours (NTE)

Base 1 February 2024 31 December 2024 1 February 2024 31 July 2024 100

1.5 Place of Performance. The designated installations for this contract are Eglin AFB and Tyndall AFB. The government will provide helicopter fuel (no oils and/or lubricants) during performance of this contract. The contractor will be present and perform all fuel sampling procedures and dispensing Jet A fuel into the contractor helicopter. Primary helibase will be Eglin AFB in Niceville, FL. The contractor is responsible for all costs of sheltering the helicopter.

The Contractor shall adhere to federal, DoD, Air Force, state, and local laws, regulations, instructions, policies, and requirements, as well as requirements of this contract.

1.6 Specific Tasks. Contractor services will include the following: a helicopter that has been inspected and approved for the mission(s) to be performed and has a current Interagency Helicopter Data Card upon contract award. Mission(s) to be performed include:

a) Passenger and cargo transport

b) Low level recon

c) External load

d) Aerial ignition

e) Fire suppression

f) Water bucket use

g) Longline/remote hook

Contractor furnished pilots are required to have an Interagency Helicopter Pilot Card showing qualifications for the mission(s) to be performed. Missions to be performed include:

a) Low level recon

b) Heli tack/passenger transport

c) External load (belly hook)

d) Water delivery

e) Longline/remote hook VTR (150 ft.)

f) Aerial ignition using a PSD machine

The Government will direct aircraft to support its missions and objectives. During aerial ignition, the contractor shall maintain the helicopter within GPS boundary parameters as briefed by the Firing Boss in pre-flight briefing.

1.7 Historical Data. Historical information is located in Appendix 2 of this PWS.

1.8 Minimum Qualifications and Requirements.

1.8.1 Item Requirement

a. Designated Base - All equipment, facilities, and personnel required under this contract shall be delivered to and removed from Eglin AFB, FL as the primary designated base.

b. Aircraft required - One Type III helicopter equivalent to a Bell 206 L-3 model or above equipped as specified in Section 1.8.2.

c. Fuel service vehicle required – None. The government will furnish the fuel. The contractor

Total flight hours not to exceed 100, but may be fewer based on weather and Government need. All 100 hours are billable even if fewer flight hours are flown. See Appendix 2 on page 34 for flight hour estimates.

will perform all fuel sampling procedures and dispense fuel into helicopter. See 1.8.5.

d. Crew compliment required – Pilot-in-Command (PIC), Relief PIC.

e. Helicopter seating - Four (4) insured passenger seats not including pilot, but including copilot seat in an aircraft, normally single-pilot operated.

f. Internal payload - non-jettisonable payload (HOGE) of 900 pounds at 30 degrees C at 2,000 feet pressure altitude using a pilot weight of 200 pounds, a 25-pound survival kit, and fuel for 2 hours. The total of 900 pounds for non-jettisonable internal HOGE payload includes the 140 pounds safety factor for load calculations.

g. Power plant - Turbine engine

h. Airspeed - 100 knots VNE at max gross weight, 2,000 feet pressure altitude and 30 degrees

C.

1.8.2 Helicopter Requirements.

a. Helicopter shall be maintained in accordance with all applicable 14 CFR requirements, mandatory manufacturers’ bulletins as required or identified by the FS and/or DOI, and all applicable FAA Airworthiness Directives (AD).

b. All required documents needed to verify the data in Form FS-5700-21a or OAS 36b;

Helicopter Data Record (including airframe logs, engine logs, compliance with mandatory manufacturer’s bulletins, FAA AD compliance, listing of installed STC’s, and helicopter status record) shall be provided to the Contracting Officer Representative when requested.

A status sheet containing the status of inspections, Airworthiness Directives and components having time/life limits will be available with the helicopter. This status sheet can be inspected at the request of the COR prior to every flight.

c. Unless authorized by an approved Minimum Equipment List (MEL), the helicopter shall not be approved or used if any accessory or instrument listed on the helicopter type certificate data sheet is inoperative. However, all items required by this contract may not be placed on an MEL as non-operational unless approved by an Aviation Maintenance Inspector. The following equipment, when inoperative, cannot be placed on an MEL with the helicopter continuing to be utilized under contract.

• Emergency Locator Transmitter

• VHF-AM Transceiver (at least one must be operational)

• P25 Digital VHF-FM Transceiver (at least one must be operational)

• Transponder and altitude reporting system (at least one must be operational)

• Static pressure, altimeter, and automatic altitude reporting system (at least one must be operational and connected to an operational transponder and altitude reporting system)

• Helicopter shall not be approved if any component time in service exceeds the manufacturers’ recommended Time Between Overhaul (TBO) or FAA- approved extension. All inspection times and intervals shall comply with the Contractor’s FAA-approved maintenance program.

• Complete set of current aeronautical charts covering an area of operation. The Contractor shall be responsible for providing navigation publications. FAA approved “electronic” flight bags meet this requirement.

d. Condition of Equipment

• Contractor-furnished aircraft and equipment shall be operable, free of damage, and in good repair. Helicopter systems and components shall be free of leaks except within limitations specified by the manufacturer.

• All windows and windshields shall be clean and free of scratches, cracks, crazing, distortion, or repairs, which hinder visibility. Repairs such as safety wire lacing and stop drilling of cracks are not acceptable permanent repairs. Prior to acceptance, all temporarily repaired windows and windshields shall have permanent repairs completed or shall be replaced.

• The helicopter interior shall be clean and neat. There shall be no unrepaired tears, rips, cracks, or other damage to the interior. The exterior finish, including the paint, shall be clean, neat, and in good condition (i.e. no severe fading or large areas of flaking or missing paint etc.). Military or other low visibility paint schemes are unacceptable. Any corrosion shall be within manufacturer or FAA acceptable limits IAW FAA Advisory Circular #43-4B.

e. Center of Gravity

• All helicopters shall be configured so that the center of gravity will remain within the FAA approved Flight Manual, IAW FAA-H-8083-1B, published limits for all load requirements and a full range of fuel conditions, including ferry with minimum crew without subtraction or addition of ballast.

• All helicopters shall be loaded such that the center of gravity will remain within allowed limit during the flight. Actual weights will be used for flight calculation.

• When the equipped weight of the helicopter, as noted by registration number in Section B, Schedule of Items changes, the Contractor shall notify the COR of the change and submit a new weight and balance as required by the Contract. This notification shall occur prior to flight.

f. General Equipment. Helicopters shall be configured with the equipment required by 14 CFR and approved for make and model furnished. In addition, the following will be required:

• A copy of the Awarded Contract and modification(s) shall remain in the helicopter during the Contract period(s).

• Instrumentation required by the Type Certificate and 14 CFR for use with the make and model furnished.

• Free air temperature gauge.

• First Aid Kit Aeronautical (Exhibit 1, First Aid Kit Aeronautical)

• Survival Kit Aeronautical (Exhibit 2, Survival Kit Aeronautical, Lower 48; weight of Survival Kit shall be considered as an addition to the equipped weight of the aircraft and will be documented on the C-chart or equipment list)

• Additional Suppression/Prescribed Fire Equipment (Exhibit 4, Additional Suppression/Prescribed Fire Equipment).

• Seat belts for all seats. One set of individual lap belts for each occupant.

• FAA-approved double-strap shoulder harness with automatic or manual locking inertia reels for each front seat occupant. Shoulder straps and lap belts shall fasten with one single-point, metal-to-metal and a quick-release mechanism. Standard factory shoulder harnesses are acceptable for Aerospatiale and Bell transport category helicopters. Military style harnesses are acceptable. (Exhibit 3, Restraint Systems Condition Inspection Guidelines).

• FAA approved shoulder harness (either single diagonal strap with inertia reel or double strap with or without inertia reel) for each aft cabin passenger position.

Shoulder harness straps and lap belts must fasten with a single-point, metal-to-metal, and quick-release mechanism.

• All Seats, Seat Belts and Shoulder Harnesses for all helicopters must either be:

An OEM installation Supplemental Type Certificate (STC) shall be kept for all helicopter modifications.

Approved for installation by a FAA Form 8110-3 with all DER supporting engineering substantiation documentation attached or Field Approved for installation with supporting FAA Form 8110-3 and all

DER supporting engineering substantiation documentation attached

• One flight hour meter (Hobbs) installed in a location observable from the cockpit.

The meter shall be wired in series with a switch on the collective control, and a switch activated by engine or transmission oil pressure. Or for helicopters with a landing gear incorporating an extendable strut, the hour meter may be activated by a switch mounted in such a manner as to only operate when the strut is fully extended. The hour meter shall record actual flight time in hours and tenths of an hour only.

• Operations from other than the manufacturer’s designated pilot station (right seat in most helicopters) are allowed only with an approved FAA Supplemental Type Certificate (STC) or field approval and designation on the aircraft Interagency Data Card. For single-piloted aircraft, field approvals in lieu of STCs are not acceptable unless the appropriate crew door has been modified with bubble window (if available) and operational gauges installed in the door that can be viewed by the pilot while performing vertical reference operations.

• Convex mirror for observation of external loads and landing gear (not required for aircraft equipped ONLY for vertical reference operations).

• The Fire extinguisher(s) shall be a hand-held bottle, fully charged, with a minimum of 1.5 pounds capacity and 2-B:C rating, maintained in accordance with NFPA 10 and mounted with a quick release attachment accessible to the flight crew while seated.

• Standard Category helicopters with a floor height greater than 18-inches shall have an approved personnel access step to assure safe entrance and exit from each door of the helicopter. A section of external cargo rack may be utilized as a step by providing a clear space covered with non-skid material. The access step shall be approved by the aircraft inspector.

• One or more independently switched white strobe light(s) mounted on top of the helicopter or otherwise visible from above. A LED aviation red strobe installed by the OEM or Supplemental Type Certificate will also fulfill this requirement. In order to meet contract specifications, Contractors shall obtain FAA approval (FAA Form 337) to alter the aircraft, if applicable. The contractor shall provide the FAA approval (FAA Form 337) to the COR at time of contract award or after approval if completed after contract award. Each anti-collision light shall be aviation red and shall meet the applicable requirements of 14 CFR Part 27.1401 or Part 29.1401.

• High visibility markings on main rotor blades (Exhibit 5, High Visibility Markings on Main Rotor Blades).

• Remote and Cargo Hook One keeperless cargo hook that is capable of being loaded and locked in a single motion with one hand and is rated at the maximum lifting capacity of the aircraft IAW aircraft manual.

As a minimum, the airframe cargo hook shall be completely disassembled and inspected with repairs made as required, lubricated, and a full-load operational check in accordance with manufacturer’s recommendations.

One remote cargo hook maintained in accordance with Exhibit 4 and a minimum of 150 feet of long line. Long line may consist of multiple segments and none shorter than 50 feet as per Exhibit 4.

• Water Bucket(s) One (1) collapsible, variable capacity water/retardant bucket shall be furnished under this Contract. The bucket must be capable of being transported in cabin or baggage compartment or external basket of the helicopter. The bucket must have a manufacturer's capacity adjustment commensurate with the maximum lifting capability of the contract aircraft.

The bucket must be capable of being operated with all increments of the longline, i.e., 50, 100, 150 feet.

An Operations Manual for the type of bucket(s) provided shall be available on site.

Shall be leak free (½ gallon or less in a 24-hour period)

• FAA Approved Extended Height /High Skid Landing Gear (if available by STC or aircraft manufacturer) IAW 14 CFR 39 and approved by the aircraft maintenance inspector.

• FAA approved high visibility, pulsating, forward facing, conspicuity lighting. Shall be verified by the aircraft maintenance inspector.

• FAA-approved locking cap(s) on all fuel filler ports. Single point refueling port dust caps need not have an FAA-approved locking device. Shall be verified by the aircraft maintenance inspector.

• Wire strike protection system (mechanical).

• FAA approved floor protection, shall be verified by the aircraft maintenance inspector. Helicopters shall have floor protection within the cargo area. Floor protection is not required within the passenger seating areas. Floor protection in both seating and cargo areas shall not be in excess of ½ inch to allow for installation of all passenger seats and access to all installed anchor points.

• Internal baggage compartment/external cargo basket/racks. Minimum of fifteen

(15) cubic feet of cargo space with isolated internal baggage compartment(s) capable of accommodating 58-inch-long shovels, rakes, and other firefighting tools (requires rear bulkhead modification of baggage compartment of some models).

External cargo basket(s)/rack(s) with a closing mechanical latching lid, if available, may be provided in lieu of baggage compartments, which cannot be modified to accept fire tools. The lid shall cover the entire basket/rack.

Cargo basket/rack shall be at least 4-inches deep and shall not hamper ingress and egress of personnel from the cabin area. The devices shall be simple in function and have the capacity of being installed quickly. All cargo will be loaded, contained and restrained in a manner that is compliant with the aircraft’s approved flight manual.

All helicopters equipped with an external basket must have a FAA STC or field approval applicable for make and model, for dimension, load carrying capability and material construction. The basket will have a hinged top with a suitable method to secure the top closed in flight, to prevent the contents from exiting.

All helicopters shall have FAA approved internal cargo area restraints or barriers which extend from the floor to the ceiling, isolating the passenger area from the cargo area (transmission wells), sliding door area and will not compromise passenger ingress and egress. Cargo behind soft passenger seats must be restrained while seats are occupied per 14 CFR Part 29 requirements.

Restraints or barriers must be capable of being removed within 15 minutes.

Restraints within the cargo area of the transmission wells shall have netting restraints only.

• Engine inlet air filtration system/particle air separator for all medium and light helicopters.

• Heating system for windshield defog.

• Kit for disposal of fuel during start-up/shut down, i.e., EPA Bell Kit, or equal, if commercially available.

1.8.3 Pilot Qualification Requirements.

a. The Contractor must provide a pilot(s) and relief pilot(s) who meets the following minimum qualifications and who possesses the required certificates and evidence of having satisfactorily passed the evaluations for the required tasks.

b. An FAA commercial pilot certificate or higher, with a rotorcraft-helicopter rating.

c. A minimum of a current second-class medical certificate, issued in accordance with 14 CFR Part 67.

d. An FAA competency check, completed in accordance with 14 CFR Part 135.293 in the same make and model as the contract aircraft.

e. All pilots will keep in their possession a current Interagency Helicopter Qualification Card for the tasks required under this contract IAW Interagency Helicopter Operations Guide (IHOG) Chapter 5 page 5-2.

f. An agency flight evaluation, to be flown at the COR’s discretion in the same make and model as the contract aircraft. The Contractor must supply the aircraft for the flight evaluation, at no expense to the Government.

g. Proficient operation of all equipment identified in Section B (e.g., water retardant bucket, GPS, longline/remote hook etc.). The contractor shall maintain an Interagency Helicopter Pilot Qualification Card and provide to COR upon request.

h. Precise placement of externally carried cargo where requested, regardless of the cable length (as specified in Section B) while operating within the helicopter's capability. Pilots must provide written evidence of their qualifications for transporting external loads appropriate to the Contractor’s 14 CFR Part 133 certification.

i. Aerial ignitions with a plastic sphere dispenser (PSD). The PSD will be supplied by the Government. The agencies may require pilots to demonstrate this proficiency during an evaluation flight in an aircraft supplied by the Contractor and at no expense to the Government.

j. Minimum Pilot in Charge (PIC) time accumulated as follows:

(a) 1,500 hours . . . in helicopters.

(b) 100 hours . . . in helicopters in the last 12 months.

(c) 100 hours . . . in the weight class of the helicopter offered. Defined as: “small” - up to an approved gross weight of 7,000 pounds; “medium” - 7,000 pounds up to 12,500 pounds; “large” - over 12,500 pounds.

(d) 100 hours . . . in turbine engine helicopters.

(e) 50 hours . . . in the same make and model as the contract helicopter. Pilot flight hour requirements in make and model may be reduced by 50 percent, if the pilot shows evidence of having satisfactorily completed the manufacturer's approved ground school and flight check in the same make, model, and series as the contract helicopter. (See the Helicopter Like Makes and Models Exhibit.)

(f) 10 hours. . . in the same make, model, and series as the contract helicopter in the last 12 months. (See the Helicopter Like Makes and Models Exhibit.)

(g) Last 90 days . . . Compliance with 14 CFR 61.57 or 135.247 as appropriate.

1.8.4 Avionics Requirements

a. The Contractor must provide, install, and maintain the following systems in accordance with the manufacturer's specifications and the installation and maintenance standards of Section B7. Detailed avionics systems performance requirements are listed in Avionics Operational Test Standards (copies available upon request from OAS Avionics, or the most recent list may be found online at:

http://www.nifc.gov/NIICD/docs/avionics/FSAMDA24E.pdf.

http://www.nifc.gov/NIICD/docs/avionics/FSAMDA24E.pdf

b. Helicopters approved under this contract, which also meet all avionics requirements (less any requirement for a 406MHz ELT) under the current OAS Fixed-Wing On- Call Air Tactical contract, may also be approved for Air Tactical missions, at the level commensurate with the aircraft's avionics equipment.

c. Avionics Installation and Maintenance Standards Strict adherence to the recommendations in the following FAA Advisory Circulars is required: AC 43.13-1B Chapter 11, "Aircraft Electrical Systems," and Chapter 12, "Aircraft Avionics Systems”; AC 43.13-2B Chapter 1, "Structural Data," Chapter 2, "Communication, Navigation, and Emergency Locator Transmitter System Installations," and Chapter 3, "Antenna Installation."

d. All avionics systems requiring an antenna must be installed with a properly matched, aircraft-certified antenna, unless otherwise specified. Antennas must be polarized as required by the avionics system and must have a voltage standing wave ratio (VSWR) of 3.0 to 1 or better.

e. Although the contract aircraft may not be certified for flight under instrument flight rules (IFR), the aircraft's static pressure system, altimeter instrument system, and automatic pressure altitude reporting system must be maintained in accordance with the IFR requirements of 14 CFR Part 91.411 and inspected and tested every 24 calendar months, as specified by 14 CFR Part 43, appendices E and F.

f. Avionics equipment mounting location and installation must not interfere with passenger safety, space, and comfort. Avionics equipment must not be mounted under seats designed for deformation during energy attenuation. In all instances, the designated areas for collapse must be protected. Avionics equipment normally operated by both pilot and observer/copilot must be mounted in the optimum location for the make, model, and series of aircraft offered. Mounting(s) which offers full and unrestricted movement of each control to both pilot and observer/copilot, when seated, without interference from clothing, cockpit structure, or flight controls, must be a goal in the selection of location.

g. Transmitters shall not open squelch on, or interfere with, other AM or FM transceivers in the aircraft which are monitoring different frequencies. So-called “Transmit Interlock” functions shall not be used with communication transceivers.

h. Communications Systems One automatic-fixed Emergency Locator Transmitter (ELT), certified under TSO-C126 (or newer) which must be installed in a conspicuous or marked location, and meet the same requirements as those detailed for airplanes in 14 CFR 91.207 (excluding section f). ELT antennas must be mounted externally to the aircraft unless installed in a location approved by the aircraft manufacturer. TSO-C126 and newer ELTs require documentation of current registration with the National Oceanic and Atmospheric Administration (NOAA), or the national civil aviation authority with which the aircraft is registered.

• One panel-mounted VHF-AM (VHF-1) aeronautical transceiver, with a minimum of 760 channels covering 118.000 to 136.975 MHz. The transceiver must have channels selectable in no greater than 25 kHz increments and a minimum of 5 watts carrier output power. The transceiver’s operational controls must be mounted so they are readily visible and accessible to the pilot.

• One P25-compliant VHF-FM transceiver. The transceiver (FM-1), must provide selection of narrowband analog (12.5 kHz) or narrowband digital (12.5 kHz) operation on each of a minimum of 100 channels. The transceiver’s operational controls must be located and arranged so that the pilot and observer/copilot when seated, have full and unrestricted movement of each control without interference from clothing, the cockpit structure, or the flight controls.

• The transceiver’s operational frequency range must include the band of 136.0000 MHz to 173.9975 MHz. The operator(s) must be able to program any usable channels within that band, along with any required CTCSS tones, National Access Codes (NAC’s), or Talk Group ID’s (TGID’s), while in flight. The transceiver must also incorporate a separate, programmable GUARD receiver, with accompanying GUARD transmit capability. Unless instructed by the Government for use on a specific project, all frequencies programmed for use under this Contract must be in the narrowband analog mode.

• Carrier output power for the transceiver must be 10 watts nominal value (original design specification). The transceiver must be capable of displaying receiver and transmitter operating frequency, alpha-numeric channel labels, and must provide both receiver and transmitter activation indicators for MAIN and GUARD.

Simultaneous monitoring of both MAIN and GUARD receivers is required.

Scanning of the GUARD frequency is not acceptable.

Prior to acceptance under this contract the COR will verify that, the transceiver be programmed with the narrowband analog GUARD receive and transmit frequencies of 168.625 MHz, with a 110.9 Hz CTCSS tone on transmit only.

• The following VHF-FM aeronautical transceivers are known to meet the above requirements:

Technisonics: TDFM-136, TDFM-136A, TDFM-136/NV, TDFM-

136A/NV, TDFM-136B, TDFM-136B/NV.

Cobham: (formerly NAT) NPX-136D-070.

i. The contractor may provide an equivalent VHF-FM aeronautical transceiver but it shall meet the above requirements.

• Provisions for auxiliary VHF-FM (AUX-FM) portable radio:

• Interface for installing and properly operating an auxiliary VHF-FM portable radio through the aircraft's audio control system(s). The interface must consist of the appropriate wiring from the audio control system, terminated in an ITT/Cannon type MS3112E12-10S 10-pin connector conveniently located for use by the observer/copilot, and utilizing the contact assignments as specified by drawing FS/AMD-17 in the exhibits.

• One weatherproof, external, broadband antenna covering the 150-174 MHz band, with associated RG-58A/U (or equivalent) coaxial cable and connector, terminated in a bulkhead-mounted, female BNC connector (type UG-290A), conveniently located for use by the observer/copilot adjacent to the above 10- pin connector (Comant model CI-177 or equal).

• Mounting facilities for securely installing the auxiliary VHF-FM portable radio in the cockpit in accordance with the FAA AC 43.13-2B specifications. Locate and arrange the mounting facilities so that a seated observer/copilot has full and unrestricted movement of the radio's controls, without interference from the 18-inch adapter cable, clothing, cockpit structure, or flight controls.

• Positive-polarity microphone excitation voltage provided to the AUX-FM system from the aircraft DC power system through a suitable resistor network. A blocking capacitor must be provided to prevent the portable radio microphone excitation voltage from entering the system. Side tone for the AUX-FM must also be provided (NAT model AA34-300, Premier model

• PA-34, or equivalent).

• In lieu of the above AUX-FM requirements, the Contractor may substitute an additional VHF-FM aeronautical transceiver (FM-3) which meets the requirements for the VHF-FM aeronautical transceiver(s) as detailed above.

• One satellite-based aircraft tracking hardware compatible with the government’s Automated Flight Following (AFF) Program (https://aff.gov). Not all available satellite-based tracking systems are compatible with the Government’s AFF Program, nor meets AFF’s requirements. The contractor must ensure that the aircraft hardware offered is compatible with AFF. For questions about current compatibility requirements contact the AFF Program Manager listed under contacts at https://www.aff.gov.

• The AFF aircraft hardware must be powered by the aircraft’s electrical system, installed per the manufacturer’s installation manual, and operational in all phases of flight. AFF aircraft hardware must utilize as a minimum: Satellite communications, an externally or internally mounted antenna, provide data to the Government’s AFF viewing software, use aircraft power via a dedicated circuit breaker for power protection, and be mounted so as to not endanger any occupant from AFF aircraft hardware during periods of turbulence. Antennas should be placed where they have the best view of the overhead sky as possible. Externally mounted antennas are recommended to improve system performance. Any visual indicators for remotely installed units must be mounted so that they can be easily viewed by the pilot. AFF communications must be fully operational in all 50 states. Contractors working in or accepting dispatches to the State of Alaska, Southern Canada, or Western Canada must have an AFF system capable of being tracked in these locations at all times.

Not all manufacturers’ AFF equipment communication links will operate effectively in all geographic areas.

• The contractor must maintain a subscription service through the AFF aircraft hardware provider allowing AFF position reporting for satellite tracking via the Government AFF viewing software. The position-reporting interval must be every two minutes while the aircraft is in flight. The contractor must register their AFF aircraft hardware with the Government through https://www.aff.gov providing:

complete tail number; manufacturer and serial number of the AFF transceiver;

aircraft make and model; and contractor contact information. If the contractor relocates previously registered AFF aircraft hardware into another aircraft, then the contractor must contact the government’s AFF Program making the appropriate changes prior to aircraft use. In all cases, the contractor must ensure that the correct aircraft information is indicated within AFF. The contractor must contact the Government of system changes, scheduled maintenance, and planned service outages.

• Registration contact information, a web accessible feedback form, and additional information is available at: https://www.aff.gov. The Fire Applications Support Desk (FASD) can be reached at (866) 224-7677 or (360) 326-6002.

• Prior to the aircraft’s annual contract inspection, the contractor must ensure compliance with all AFF systems requirements. The contractor must additionally perform an operational check of the system. As a minimum, the operational check must consist of confirming the aircraft being tested is displayed in AFF (indicating it is currently transmitting data to AFF) and that all information displayed in AFF is current. A username and password are required to access AFF. Log on to the AFF website at https://www.aff.gov to request a username and password, or contact the

FASD.

• AFF becomes inoperable/unreliable the aircraft may, at the discretion of the Government, remain available for service utilizing radio/voice system for flight following. The contractor will return the AFF system to full operational capability within 72 hours after the inoperative/unreliable unit is first discovered as defective.

• The contractor shall follow the requirements set forth in the USDA Forest Service Automated Flight Following Specification Section Supplement, included in Appendix 5 of this PWS.

i. Navigational Systems https://www.aff.gov/ http://www.aff.gov/ http://www.aff.gov/ http://www.aff.gov/

• One permanently installed, panel-mounted global positioning system (GPS-1) utilizing an approved, fixed external aircraft antenna and powered by the aircraft electrical system or an aviation portable GPS unit (Garmin GPS Map 296/396/496 or equivalent) provided the portable unit is securely mounted, is equipped with a remote (i.e., not part of the GPS unit) antenna, and presents information from an overhead orientation (not a drive-along-the-road type), and is powered by the aircraft electrical system. The GPS (permanently installed or portable) must utilize the WGS-84 datum and reference latitude and longitude coordinates in the degrees/minutes/decimal minutes (DM) mode for aircraft positioning. The GPS navigation database must be updated annually covering the geographic areas where the aircraft will operate.

j. Audio Systems

• Two separate audio control systems (which may be combined in a single unit) for the pilot and observer/co-pilot to select receiver audio outputs and transmitter microphone/push to talk (PTT) audio inputs for all installed radios and public address (PA) systems. Each system must also allow the pilot and observer/copilot to independently adjust both the intercommunications system (ICS) and the receiver audio output levels.

• Transmitter selection and operation. Separate transmitter selection controls must be provided for both the pilot’s and observer/copilot’s microphone/PTT inputs. The system must be configured so the pilot and observer/copilot may each simultaneously select and utilize a different transmitter (or PA system when installed) via their respective microphone/PTT. Whenever a transmitter is selected, the companion receiver audio must automatically be selected for the corresponding earphone. Transmitter side tone audio must be provided for the user as well as for cross-monitoring via the corresponding receiver selection switch on the other audio control system.

• Receiver selection and operation. Separate controls must be provided for both pilot and observer/copilot to select audio from one or any combination of available receivers. The ICS-equipped aft passenger positions must monitor the receiver(s) as selected by the observer/copilot. The receiver audio output must be free of excessive distortion, hum, noise, and crosstalk, and must be amplified sufficiently to facilitate ease of use in a noisy cockpit/cabin environment.

• The audio system(s) controls must be located and arranged so that both the pilot and observer/copilot, when seated, have full movement of their respective controls without interference from their clothing, the cockpit structure, or the flight controls.

Labeling and marking of controls must be clear, understandable, legible, and permanent. Electronic label maker marking is acceptable.

• An internal communication system (ISC) for the pilot, observer/copilot, and the two aft cabin exit positions. ICS audio must mix with, but not mute, selected receiver audio. An ICS audio level control must be provided for each position above.

Adjustment of the ICS audio level at any position must not affect the level at any other position. A "hot mic" capability, controlled via an activation switch or voice activation (VOX), must be provided for the pilot and copilot/observer positions. ICS side tone audio must be provided for the earphones corresponding with the microphone in use. The ICS audio output must be free of excessive distortion, hum, noise, and crosstalk and must be amplified sufficiently to facilitate ease of use in a noisy cockpit/cabin environment.

• Earphones, microphones, PTT’s, and jacks designed for operation with 600- ohm earphones and carbon-equivalent, noise-canceling boom type microphones (Gentex electret type model 5060-2, military dynamic type M- 87/AIC with type CE-100 TR preamplifier, or equivalent) with U-174/U (single/male) type connector plug. The pilot position only may be configured for low impedance (dynamic) operation.

• All earphone/microphone jacks in the aircraft (except the pilot's) must be U- 92A/U

(single/female) type, which will accept U-174/U type plugs.

• Separate PTT switches for radio transmitter and ICS microphone operation must be provided at the pilot, observer/copilot, and any other positions required above to be furnished with both radio transmitter and ICS operation. The pilot's PTT switches must be mounted on the cyclic control. The observer/copilot's and any other required position’s PTT switches must be mounted on the cord to the earphone/microphone connector. The aft cabin positions must be furnished with cord-mounted ICS PTT switches.

k. Other Avionics

• One air traffic control (ATC) transponder and altitude reporting system meeting the requirements of 14 CFR Part 91.215 (a) and (b), and inspected and tested every 24 months in accordance with 14 CFR 91.413.

• The Contractor shall furnish a cellular telephone for use by the PIC. The cellular telephone shall be provided with service to the area of the contiguous 48 States.

Each cellular telephone shall be equipped with both 110VAC and 12VDC adapter cord assemblies for charging use. The Contractor shall provide the number of the cellular telephone to Government personnel when requested.

• Automatic Dependent Surveillance – Broadcast (ADS-B)

• Effective no later than January 1, 2020, all aircraft must be equipped to meet the

ADS-B OUT requirements of 14 CFR 91.225. ADS-B OUT systems must be approved to either TSO-C154c (978MHz Universal Access Transceiver [UAT]) or TSO-C166b (1090MHz Extended Squitter [1090ES]). Aircraft operating outside of the United States must be equipped with systems approved to TSO-C166b.

• ADS-B IN systems are not required, but any such system furnished must be TSO-approved, use diversity antennas on both the top and bottom of the aircraft, receive both UAT and 1090ES, and be interfaced to a multifunction display (MFD) capable of displaying TIS-B traffic and FIS-B weather.

• Each aircraft must be equipped to meet the Radio Altimeter requirements of 14 CFR 135.160, unless a letter of deviation authority has been issued by an FAA Administrator.

1.8.5 Fuel Servicing Vehicle Requirements.

None.Dry rate: The government will provide a fuel truck and all fuel. The contractor will be responsible for performing all fuel sampling procedures and dispensing fuel into the helicopter during the contract period. The contractor will be responsible for all lubricating oils required to operate all equipment during the contract period.

1.8.6 Maintenance Requirements.

General – Maintenance. The Contractor must ensure that the aircraft and all required equipment are operated maintained in accordance with the original equipment manufacturers (OEM) or approved Standard Type Certificate (STC) holder’s current maintenance instructions including appliances, emergency equipment, and all instructions for continued airworthiness (ICA’s).

• Airworthiness Directives (AD’s) and Manufacturer's Mandatory Service Bulletins (MMSB’s)

• The Contractor must comply with all applicable MMSB’s and FAA AD’s before and during contract performance.

• The Contractor shall provide and make available a list of “issued” MMSBs and FAA ADs identifying all those that are applicable and non-applicable to the contract aircraft in the format shown in AC 43-9C, Appendix 1, complete with authorized signature, certificate, type and number. This list must include all accessories and equipment installed in each aircraft offered. Signatures of persons verifying accuracy of the list is required. The contractor shall provide the requested information to the COR upon request.

a. Manuals/Records

1. The Contractor must ensure that all contract aircraft maintenance is recorded in accordance with 14 CFR Parts 43, 91, and 135 (reference 14 CFR Parts 43.9, 43.11, 91.417, and 135.439) and that a copy of the aircraft's record is kept with the aircraft. Electronic copies of manuals and records are acceptable.

2. If requested by the Government, the Contractor must furnish to the Contracting Officer’s Representative (COR) a copy of the Contractor's procedures manuals, as outlined in 14 CFR Part 135.21, along with any revisions made during the contract period.

3. Before the start date of the contract, the Contractor must ensure that all maintenance deficiencies have been corrected or deferred in accordance with the operator's accepted/approved maintenance program. Deferred discrepancies will be evaluated and the aircraft approved for contract use on a case-by-case basis. The Contractor must correct deficiencies that occur during contract performance in accordance with the appropriate Federal Aviation Regulations (FAR) or the approved maintenance program.

b. Maintenance

1. All maintenance, including inspection, rebuilding, alteration, and installation must be accomplished by an FAA licensed mechanic who is authorized to perform maintenance in accordance with 14 CFR Part 43. The PIC shall verify only authorized personnel are performing maintenance tasks.

2. The Contractor must ensure that a mechanic who meets the contract qualification requirements inspects the contract helicopter in accordance with the procedures outlined in the operator’s FAA-approved/accepted maintenance program. Aircraft time-in-service must be recorded.

3. All aircraft maintenance log book entries shall include the title of the current maintenance publication, chapter, page and paragraph that were referenced to perform any installation, overhaul, major repair, or replacement of any engine, power train, rotor system, or flight control system. Adherence to this requirement shall begin the date of contract award and continue through the duration of the contract.

4. When any unscheduled maintenance or repairs are performed for mechanical or equipment deficiencies, a DOI/USFS approved Maintenance Inspector and the Contracting Officer will be notified for “Return to Contract Availability” before the aircraft may again be allowed to fly under the contract. Depending on the complexity of the maintenance or repair, “Return to Contract Availability” may be given by electronic or verbal means.

5. Routine/preventative maintenance must be performed before or after the Government’s scheduled daily use period or as approved by the Contracting Officer’s Representative (COR).

6. The cargo hook must be maintained in accordance with the manufacturer’s operating and maintenance instructions. If there is no hook manufacturers recommended maintenance and overhaul program, completely disassemble, inspect, repair as required, lubricate, and perform a full-load operational check every 24 calendar months. All cargo hook maintenance inspections and repair must be documented.

7. The fire extinguisher must be maintained in accordance with NFPA 10:

Standards for Portable Fire Extinguishers, or the Contractor’s 135 operations manual.

c. Maintenance Test Flight

1. The Contractor must, at their own expense, perform a functional maintenance check flight following installation, overhaul, major repair, or replacement of any engine, power train, rotor system, flight control system, or when requested by the Contracting Officer Representative (COR) and/or Contracting Officer (CO). This must be accomplished before the aircraft resumes service under the contract.

2. The Contractor must immediately notify the COR of any change to any engine, power train, flight control or major airframe component or of any major repair following an incident or accident and must describe the circumstances involved.

3. When any unscheduled maintenance or repairs are performed for mechanical or equipment deficiencies, a DOI/USFS approved Maintenance Inspector and the Contracting Officer will be notified for “Return to Contract Availability” before the aircraft may again be allowed to fly under the contract. Depending on the complexity of the maintenance or repair, “Return to Contract Availability” may be given by electronic or verbal means.

d. Time Between Overhaul (TBO) and Life-Limited Parts

1. All components, including engines, must be replaced upon reaching the factory-recommended TBO or FAA-approved extension IAW FAA Advisory Circular 120-113. Life-limited parts must be replaced at the specified time-in-service hours or cycles.

2. Aircraft operated with components or accessories on approved TBO extension programs are acceptable provided (1) the Contractor is the holder of the approved extension authorization (not the owner if the aircraft is leased) and

(2) the Contractor operates in accordance with the extension authorization.

3. The Contractor must supply, at the time of the initial agency inspection, a list of all items installed on the aircraft that are required to be overhauled or replaced on a specified time basis. This list must include the component’s name, part number, serial number, total time, service life (or inspection/overhaul time interval), and time and date when the component was overhauled, replaced, or inspected.

e. Weight and Balance

1. The aircraft's required weight and balance data must be determined by actual weighing of the aircraft within 24 calendar months preceding the starting date of the contract, or renewal period, and following any major repair or major alteration or change to the equipment list which significantly affects the center of gravity of the aircraft.

2. All aircraft must be weighed on scales that have been certified as accurate within the preceding 24 calendar months. Any FAA accredited weights and measures laboratory may serve as the certifying agency.

3. The Contractor must compile a list of equipment installed in the aircraft at the time of weighing. Each page of the equipment list must identify the specific aircraft by its serial and registration numbers and must be dated to indicate the last date of weighing or computation. Items which may be easily removed or installed for aircraft configuration changes (seats, doors, radios, cargo hook, baskets, special mission equipment, etc.) must also be listed including the name, the weight and arm of each item. The weight and balance must be revised each time new equipment is installed or old equipment is removed.

Weight and balance procedures under 14 CFR Parts 23.29 and 23.1589 are acceptable.

f. Turbine Engine Power Assurance Checks

1. On the first day of operation and no more than each 10 hours of operation thereafter, the Contractor shall perform a power assurance check in accordance with the helicopter flight manual (pilot’s operating handbook) or approved company performance monitoring program.